KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 100,000 Max Cl/Cd: 50.32 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135b-il-100000.txt Download as CSV file: xf-kc135b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL124.32 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4812 0.09472 0.08974 -0.0349 1.0000 0.1153
-9.750 -0.5109 0.08833 0.08345 -0.0421 1.0000 0.1175
-9.500 -0.5467 0.08378 0.07890 -0.0457 1.0000 0.1181
-9.250 -0.5824 0.08134 0.07644 -0.0442 1.0000 0.1185
-9.000 -0.5314 0.07603 0.07128 -0.0441 1.0000 0.1271
-8.750 -0.5553 0.07294 0.06821 -0.0429 1.0000 0.1291
-8.500 -0.5829 0.07028 0.06549 -0.0409 1.0000 0.1318
-8.250 -0.6306 0.07037 0.06525 -0.0360 1.0000 0.1346
-8.000 -0.5999 0.06413 0.05938 -0.0365 1.0000 0.1420
-7.750 -0.6190 0.06259 0.05773 -0.0326 1.0000 0.1480
-7.500 -0.6697 0.06528 0.05994 -0.0238 1.0000 0.1508
-7.250 -0.6415 0.05834 0.05357 -0.0244 1.0000 0.1592
-6.500 -0.6773 0.05322 0.04834 -0.0123 1.0000 0.1874
-5.250 -0.5809 0.04011 0.03530 -0.0136 0.9703 0.3396
-5.000 -0.4935 0.03446 0.02616 -0.0187 0.9640 0.1005
-4.750 -0.4588 0.03263 0.02377 -0.0186 0.9569 0.0869
-4.500 -0.4216 0.03043 0.02132 -0.0203 0.9516 0.0859
-4.250 -0.3849 0.02856 0.01923 -0.0218 0.9464 0.0845
-4.000 -0.3513 0.02707 0.01758 -0.0225 0.9397 0.0835
-3.750 -0.3083 0.02571 0.01610 -0.0251 0.9355 0.0849
-3.500 -0.2768 0.02505 0.01529 -0.0256 0.9287 0.0885
-3.250 -0.2432 0.02346 0.01390 -0.0267 0.9231 0.0923
-3.000 -0.2048 0.02251 0.01304 -0.0288 0.9189 0.1006
-2.750 -0.1880 0.02193 0.01247 -0.0270 0.9100 0.1074
-2.500 -0.1564 0.02118 0.01167 -0.0279 0.9046 0.1221
-2.250 -0.1345 0.02046 0.01106 -0.0271 0.8975 0.1546
-2.000 -0.1388 0.01855 0.01140 -0.0208 0.8894 0.6560
-1.750 -0.1216 0.01908 0.01226 -0.0156 0.8841 0.7691
-1.500 -0.1077 0.01964 0.01286 -0.0112 0.8760 0.8102
-1.250 -0.0705 0.02024 0.01344 -0.0105 0.8722 0.8501
-1.000 -0.0072 0.02125 0.01436 -0.0138 0.8709 0.8863
-0.750 0.0344 0.02177 0.01480 -0.0160 0.8649 0.9015
-0.500 0.0844 0.02182 0.01473 -0.0206 0.8599 0.9055
-0.250 0.1366 0.02173 0.01454 -0.0255 0.8562 0.9103
0.000 0.1633 0.02190 0.01466 -0.0262 0.8489 0.9190
0.250 0.2133 0.02192 0.01464 -0.0309 0.8437 0.9234
0.500 0.2599 0.02181 0.01447 -0.0347 0.8396 0.9296
0.750 0.2948 0.02204 0.01471 -0.0371 0.8320 0.9371
1.000 0.3414 0.02188 0.01453 -0.0408 0.8256 0.9431
1.250 0.3786 0.02186 0.01452 -0.0430 0.8174 0.9510
1.500 0.4261 0.02155 0.01421 -0.0467 0.8091 0.9571
1.750 0.4637 0.02149 0.01418 -0.0489 0.7992 0.9655
2.000 0.5091 0.02111 0.01382 -0.0520 0.7915 0.9725
2.250 0.5501 0.02087 0.01362 -0.0548 0.7791 0.9807
2.500 0.5926 0.02040 0.01320 -0.0574 0.7660 0.9889
2.750 0.6371 0.01991 0.01273 -0.0604 0.7544 0.9971
3.000 0.6622 0.01967 0.01252 -0.0602 0.7438 1.0000
3.250 0.6709 0.01975 0.01267 -0.0575 0.7320 1.0000
3.500 0.6827 0.01967 0.01262 -0.0548 0.7214 1.0000
3.750 0.6979 0.01947 0.01242 -0.0524 0.7112 1.0000
4.000 0.7073 0.01952 0.01251 -0.0493 0.6982 1.0000
4.250 0.7204 0.01948 0.01251 -0.0465 0.6855 1.0000
4.500 0.7375 0.01930 0.01238 -0.0441 0.6724 1.0000
4.750 0.7566 0.01905 0.01216 -0.0419 0.6584 1.0000
5.000 0.7756 0.01879 0.01193 -0.0396 0.6427 1.0000
5.250 0.7947 0.01849 0.01169 -0.0373 0.6245 1.0000
5.500 0.8157 0.01808 0.01130 -0.0351 0.6042 1.0000
5.750 0.8341 0.01776 0.01102 -0.0326 0.5790 1.0000
6.000 0.8517 0.01748 0.01073 -0.0299 0.5476 1.0000
6.250 0.8680 0.01732 0.01048 -0.0270 0.5076 1.0000
6.500 0.8806 0.01750 0.01048 -0.0238 0.4580 1.0000
6.750 0.8911 0.01799 0.01066 -0.0204 0.4076 1.0000
7.000 0.9004 0.01874 0.01106 -0.0171 0.3640 1.0000
7.250 0.9100 0.01962 0.01164 -0.0141 0.3289 1.0000
7.500 0.9211 0.02051 0.01235 -0.0115 0.2992 1.0000
7.750 0.9330 0.02135 0.01311 -0.0090 0.2733 1.0000
8.000 0.9440 0.02219 0.01381 -0.0065 0.2498 1.0000
8.250 0.9532 0.02296 0.01459 -0.0038 0.2250 1.0000
8.500 0.9600 0.02390 0.01546 -0.0007 0.1992 1.0000
8.750 0.9630 0.02505 0.01648 0.0027 0.1704 1.0000
9.000 0.9633 0.02638 0.01762 0.0065 0.1431 1.0000
9.250 0.9654 0.02775 0.01885 0.0100 0.1215 1.0000
9.500 0.9726 0.02922 0.02015 0.0126 0.1068 1.0000
9.750 0.9833 0.03062 0.02154 0.0146 0.0954 1.0000
10.000 1.0016 0.03230 0.02326 0.0157 0.0871 1.0000
10.250 1.0254 0.03425 0.02507 0.0159 0.0799 1.0000
10.500 1.0400 0.03580 0.02685 0.0174 0.0746 1.0000
10.750 1.0759 0.03860 0.02951 0.0155 0.0690 1.0000
11.000 1.0829 0.04027 0.03157 0.0181 0.0662 1.0000
11.250 1.0951 0.04235 0.03387 0.0196 0.0634 1.0000
11.500 1.1082 0.04477 0.03649 0.0209 0.0613 1.0000
11.750 1.1310 0.04836 0.04013 0.0202 0.0588 1.0000
12.000 1.1254 0.05107 0.04315 0.0234 0.0579 1.0000
12.250 1.1124 0.05334 0.04577 0.0269 0.0572 1.0000
12.500 1.1014 0.05635 0.04909 0.0295 0.0569 1.0000
12.750 1.0865 0.05959 0.05263 0.0316 0.0567 1.0000
13.000 1.0663 0.06312 0.05645 0.0331 0.0561 1.0000
13.250 1.0479 0.06728 0.06087 0.0338 0.0563 1.0000
13.500 1.0268 0.07188 0.06569 0.0337 0.0566 1.0000
13.750 1.0035 0.07706 0.07108 0.0329 0.0569 1.0000
14.000 0.9779 0.08292 0.07713 0.0311 0.0572 1.0000
14.250 0.9522 0.08947 0.08384 0.0284 0.0576 1.0000
14.500 0.9279 0.09659 0.09108 0.0252 0.0581 1.0000
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Polar data table (+)
Polar graphs
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